Hypersonic Similarity Parameter Calculator

✖Mach number is a dimensionless quantity representing the ratio of flow velocity past a boundary to the local speed of sound.ⓘ Mach Number [M]			+10% -10%
✖Flow Deflection angle is defined as the angle by which the flow turns towards the oblique shock.ⓘ Flow Deflection angle [θ]			+10% -10%

✖Hypersonic Similarity Parameter, In the study of hypersonic flow over slender bodies, the product M1u is an important governing parameter, where, as before. It is to simplify the equations.ⓘ Hypersonic Similarity Parameter [K]

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Hypersonic Similarity Parameter Solution

STEP 0: Pre-Calculation Summary

Formula Used

Hypersonic Similarity Parameter = Mach Number*Flow Deflection angle
K = M*θ
This formula uses 3 Variables

Variables Used

Hypersonic Similarity Parameter - (Measured in Radian) - Hypersonic Similarity Parameter, In the study of hypersonic flow over slender bodies, the product M1u is an important governing parameter, where, as before. It is to simplify the equations.
Mach Number - Mach number is a dimensionless quantity representing the ratio of flow velocity past a boundary to the local speed of sound.
Flow Deflection angle - (Measured in Radian) - Flow Deflection angle is defined as the angle by which the flow turns towards the oblique shock.

STEP 1: Convert Input(s) to Base Unit

Mach Number: 3.78 --> No Conversion Required
Flow Deflection angle: 0.53 Radian --> 0.53 Radian No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

K = M*θ --> 3.78*0.53

Evaluating ... ...

K = 2.0034

STEP 3: Convert Result to Output's Unit

2.0034 Radian --> No Conversion Required

FINAL ANSWER

2.0034 Radian <-- Hypersonic Similarity Parameter

(Calculation completed in 00.004 seconds)

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Created by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

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National Institute Of Technology (NIT), Hamirpur

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< Hypersonic Flow Parameters Calculators

Coefficient of Pressure with Similarity Parameters

LaTeX Go Pressure Coefficient = 2*Flow Deflection angle^2*((Specific Heat Ratio+1)/4+sqrt(((Specific Heat Ratio+1)/4)^2+1/Hypersonic Similarity Parameter^2))

Deflection Angle

LaTeX Go Deflection Angle = 2/(Specific Heat Ratio-1)*(1/Mach Number ahead of Shock-1/Mach Number Behind Shock)

Coefficient of Drag

LaTeX Go Drag Coefficient = Drag Force/(Dynamic Pressure*Area For Flow)

Axial Force Coefficient

LaTeX Go Coefficient of Force = Force/(Dynamic Pressure*Area For Flow)

Hypersonic Similarity Parameter Formula

LaTeX Go

Hypersonic Similarity Parameter = Mach Number*Flow Deflection angle
K = M*θ

What is similarity parameter?

Similarity parameters mean some independent dimensionless parameter groups that represent the quantitative characteristics of physical similarity

How to Calculate Hypersonic Similarity Parameter?

Hypersonic Similarity Parameter calculator uses Hypersonic Similarity Parameter = Mach Number*Flow Deflection angle to calculate the Hypersonic Similarity Parameter, Hypersonic Similarity Parameter formula is defined as a dimensionless quantity used to characterize the hypersonic flow regime, providing a measure of the similarity between different flow fields, and is essential in the study of high-speed aerodynamics and aerospace engineering. Hypersonic Similarity Parameter is denoted by K symbol.

How to calculate Hypersonic Similarity Parameter using this online calculator? To use this online calculator for Hypersonic Similarity Parameter, enter Mach Number (M) & Flow Deflection angle (θ) and hit the calculate button. Here is how the Hypersonic Similarity Parameter calculation can be explained with given input values -> 4.24 = 3.78*0.53.

FAQ

What is Hypersonic Similarity Parameter?

Hypersonic Similarity Parameter formula is defined as a dimensionless quantity used to characterize the hypersonic flow regime, providing a measure of the similarity between different flow fields, and is essential in the study of high-speed aerodynamics and aerospace engineering and is represented as K = M*θ or Hypersonic Similarity Parameter = Mach Number*Flow Deflection angle. Mach number is a dimensionless quantity representing the ratio of flow velocity past a boundary to the local speed of sound & Flow Deflection angle is defined as the angle by which the flow turns towards the oblique shock.

How to calculate Hypersonic Similarity Parameter?

Hypersonic Similarity Parameter formula is defined as a dimensionless quantity used to characterize the hypersonic flow regime, providing a measure of the similarity between different flow fields, and is essential in the study of high-speed aerodynamics and aerospace engineering is calculated using Hypersonic Similarity Parameter = Mach Number*Flow Deflection angle. To calculate Hypersonic Similarity Parameter, you need Mach Number (M) & Flow Deflection angle (θ). With our tool, you need to enter the respective value for Mach Number & Flow Deflection angle and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

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